| 摘要 |
A lightweight, impact-resistant gas turbine blade, such as an aircraft engine fan blade, has an airfoil portion which includes a metal section and at least one foam section which together define a generally airfoil shape. The metal section extends from generally the blade root to generally the blade tip. A composite skin generally completely surrounds, and is bonded to, the metal section and the at-least-one foam section. Preferably, an erosion coating generally completely surrounds, and is bonded to, the composite skin.
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